US8128357B2 - Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine - Google Patents

Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine Download PDF

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Publication number
US8128357B2
US8128357B2 US12/225,933 US22593307A US8128357B2 US 8128357 B2 US8128357 B2 US 8128357B2 US 22593307 A US22593307 A US 22593307A US 8128357 B2 US8128357 B2 US 8128357B2
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United States
Prior art keywords
platform
stator blade
fastening
airfoil
blade segment
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related, expires
Application number
US12/225,933
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English (en)
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US20090304503A1 (en
Inventor
Katharina Bergander
Georg Bostanjoglo
Tobias Buchal
Winfried Eβer
Dirk Goldschmidt
Torsten Koch
Rudolf Küperkoch
Thorsten Mattheis
Jan Münzer
Ralf Müsgen
Matthias Oechsner
Ursula Pickert
Volker Vosberg
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Siemens AG
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Siemens AG
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Publication date
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Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOSTANJOGLO, GEORG, BERGANDER, KATHARINA, MUENZER, JAN, KOCH, TORSTEN, GOLDSCHMIDT, DIRK, OECHSNER, MATTHIAS, BUCHAL, TOBIAS, KUEPERKOCH, RUDOLF, MATTHEIS, THORSTEN, MUESGEN, RALF, VOSBERG, VOLKER, EBER, WINFRIED, PICKERT, URSULA
Publication of US20090304503A1 publication Critical patent/US20090304503A1/en
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Expired - Fee Related legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238—Soldering
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the invention relates to a stator blade segment of a thermal turbomachine, especially a gas turbine, with at least one profiled blade airfoil which is arranged on a platform, wherein a number of fastening elements for fastening the stator blade segment on an associated stator blade carrier are arranged on the essentially flat side of the platform which faces away from the blade airfoil.
  • Gas turbines are used in many fields for driving generators or driven machines.
  • the energy content of a fuel is used for creating a rotational movement of a turbine shaft.
  • the fuel is combusted in a combustion chamber, wherein compressed air is supplied by an air compressor.
  • the operating medium, at high pressure and at high temperature, which is produced in the combustion chamber as a result of the combustion of the fuel, is guided through a turbine unit, which is connected downstream to the combustion chambers, where the operating medium expands, performing work.
  • a number of rotor blades which are customarily assembled into blade groups or blade rows, are arranged on this turbine shaft and via an impulse transfer from the flow medium drive the turbine shaft.
  • stator blade rows which are connected to the turbine casing are customarily arranged between adjacent rotor blade rows.
  • the turbine blades customarily have a profiled blade airfoil extended along a blade axis and upon which a platform, which extends transversely to the blade axis, is formed onto the end face for fastening the turbine blade on the respective carrier body.
  • the upper side of the platform which faces the blade airfoil forms an outer delimiting surface for the flow passage of the gas turbine which guides the hot gas.
  • the platform of the respective stator blade customarily has a number of hook-like fastening elements on its underside or rear side which faces away from the blade airfoil.
  • a similar type of hook fastening of a guide ring which bridges the axial gap of two stator blades of adjacent turbine stages is known for example from EP 1 505 259 A1.
  • the stator blade with its fastening elements or fastening hooks is inserted, aligned and then fixed in a suitable manner, for example by means of caulking plates, in corresponding locating slots of a stator blade carrier.
  • an additional fastener is also provided, by means of which the hook of the guide ring can be further clamped in the stator blade carrier.
  • the stator blade comprises an inner platform upon which a flange, which extends transversely to it, is welded.
  • the flange which is provided with a hole, is fastened in a non-positive-locking manner on a support structure by means of a screw which extends through the hole.
  • stator blade airfoils of a stator blade row which are adjacent to each other in the circumferential direction of the gas turbine, can also be arranged on a common platform, so that the complete blade unit, which is subsequently referred to as a stator blade segment, can be inserted axially or in the circumferential direction into the associated stator blade carrier by means of the fastening hooks on the platform side.
  • stator blade segment in the following text, especially also in the claims, is always to also include the case of an individual stator blade with only one blade airfoil, provided that this is not specifically excluded.
  • the stator blade or the complete stator blade segment is customarily produced within the scope of a casting process so that the platform and the fastening elements on the platform side are integral co-cast component parts of the stator blade or of the stator blade segment.
  • a so-called wax model of the blade or of the blade segment is manufactured and then provided with a ceramic coating as a result of repeated immersing in a ceramic mass.
  • the wax model which is provided with the ceramic coating is burned out, wherein the ceramic hardens and the liquefied or evaporated wax is removed.
  • the negative casting mold of ceramic which is obtained in this way is finally cast with the metal blade material.
  • ceramic core elements which possibly still remain in the blade body and which were previously introduced for the forming of cavities or cooling passages which are integrated in the blade bodies are removed by leaching with caustic soda or the like.
  • the fastening elements which project like a hook from the platform, create difficulties within the scope of the manufacturing process in several aspects.
  • the production of the wax model is already relatively complicated since for forming the fastening hooks comparatively complex wax molds with a large number of so-called masking elements or slides are required.
  • the fastening hooks represent problem areas with regard to casting technique, since the undercuts when constructing the mold shells can only be poorly sanded and during the subsequent casting process, on account of their exposed position, are always prone to the formation of blowhole fields, i.e. to material defects which are created as a result of heat shrinkage in the component as it cools down.
  • the invention is therefore based on the object of disclosing a stator blade segment of the type mentioned in the introduction which, with a manufacture which is kept simple and inexpensive, and avoiding problem zones related to casting technique, is designed for an especially reliable and secure fastening on an associated stator blade carrier. Furthermore, a method which is suitable for the production of the stator blade segment is to be disclosed.
  • the object is achieved by at least one section of at least one of the fastening elements being a separately produced component which is connected in a fixed manner to the side of the platform which faces away from the blade airfoil.
  • the invention in this case is based on the consideration that the casting material for the stator blade segment should be customarily optimized for a high resistance to high temperature in order to thus ensure a high operational safety and structural stability and also a service life which is as long as possible of the sections which are directly exposed to the hot operating medium, especially of the blade airfoils which project into the flow passage of the gas turbine and of the upper side of the platform which faces the flow passage.
  • the respective fastening element comprises a connecting element which is provided with a bearing surface.
  • the connecting element is expediently constructed in the style of a flat connecting plate with a flat bearing surface.
  • the connecting element or the connecting plate can be arranged in a recessed manner in a corresponding recess of the platform, wherein as a result of this a stator blade segment which is simple to produce can especially be disclosed since the geometry of the stator blade segment hooks which is difficult to access for the casting production has been eliminated.
  • stator blade segment In the case of this at least two-component construction of the stator blade segment, not only the material selection for the fastening elements with regard to the requirements of the “hooked” fastening on the stator blade carrier can be optimized, for example with regard to load input, wear and/or sealing; furthermore, for example, the difficulties which are described in the introduction when producing the wax model or during the casting process are also dispensed with. Despite the additional manufacturing step which accompanies the joining process, the manufacture of the stator blade segment is altogether considerably simpler as a result.
  • the respective fastening element comprises a fastening hook which projects from the platform, is bent down at an angle, and which in its shape and contour is adapted to the associated locating slot of a stator blade carrier.
  • An essentially straight profiled section, which can be inserted into a polygon-like locating slot in the turbine casing, represents a possible alternative to this.
  • the connecting element is advantageously fixed in a positive-locking manner in a recess or slot of the platform which is matched to the shape of the connecting element.
  • a positive-locking connection for example is provided by the platform in the edge region of the recess or of the slot having a number of projections which grip round the connecting element in each case on its side which faces away from the bearing surface.
  • the connecting element is then inserted sideways into the recess or into the locating slot of the platform and then in a suitable manner, for example in a positive-locking, non-positive-locking and/or materially-bonding manner, fixed against slipping out sideways. Since the connecting forces are absorbed essentially by means of the projections which grip round the connecting element in a positive-locking manner, the additional fixing needs only to be designed for comparatively low loads.
  • a materially-bonding connection preferably by soldering or welding, can also be provided.
  • the respective fastening element for a high mechanical load-bearing capability, is preferably produced integrally from a single-component workpiece.
  • the fastening hook can be milled or extruded as a straight profiled section and, in a second working step, bent into the required radius.
  • the fastening element is preferably produced from a material which in comparison to the remaining stator blade segment is less resistant to high temperature but on the other hand is tougher.
  • the stator blade or the stator blade segment expediently has a multiplicity of fastening elements, wherein each of the fastening elements is preferably a component which is separately produced and designed in the manner which is described above.
  • a gas turbine customarily has a plurality of turbine stages, wherein each of the turbine stages comprises a large number of stator blades which are arranged in the circumferential direction around the flow passage on the turbine casing and collectively form a stator blade row.
  • a plurality of adjacent stator blades can be grouped together in each case for forming a stator blade segment or a “multiple”.
  • Each of the stator blades or each stator blade segment expediently has a platform with hook-like fastening elements, wherein the specifications for the hooking profile with regard to bend angle and/or bend radius as a rule vary with the installed position, i.e. especially depend upon the turbine stage or upon the stator blade row.
  • a normalized or standardized construction of the connecting elements and of the corresponding slots or recesses on the platform side, by means of which the fastening elements are connected to the respective platform, is especially advantageous in this connection.
  • the respective profiled section from which the fastening hook is created by bending can look the same in the original “raw state” for all the fastening elements.
  • One and the same fastening element therefore, in principle can be used for all the turbine stages of a turbine; only the bend radius and/or the bend angle of the fastening hook has to be adapted to the respective place of installation or to the respective intended purpose.
  • the bending of the profiled section is expediently carried out before connecting the connecting element to the platform of the stator blade segment because this makes the handling and the carrying out of the bending process easier.
  • the material selection for the fastening element can be optimized for the hooking requirements, especially with regard to load input, wear and/or sealing.
  • stator blade or of the stator blade segment becomes altogether considerably simpler.
  • Tolerances can be more simply established or met.
  • a hooking profile can be used as standard for largely all the turbine stages/performance classes and by means of different bend radii can be adapted to the respective intended purpose.
  • the wax molds for the stator blades become simpler, having fewer inserts or slides.
  • FIG. 1 shows a stator blade with a fastening element according to a first embodiment
  • FIG. 2 shows a stator blade with a fastening element according to a second embodiment
  • FIG. 3 shows a stator blade with a fastening element according to a third embodiment.
  • the stator blade 2 which is shown in FIG. 1 in a schematic side view in detail and partially sectioned, comprises a profiled blade airfoil 6 which extends in the direction of the blade axis 4 and onto which a platform 8 , which is orientated essentially transversely to the blade axis 4 , is formed in the region of the blade root.
  • the “upper side” 10 of the platform 8 which is oriented towards the blade airfoil 6 forms an outer limit of a hot gas-guiding flow passage in a gas turbine (not shown).
  • a number of hook-liked fastening elements 14 by means of which the stator blade 2 is suspended/fastened in an associated stator blade carrier (not shown) on the turbine casing, are located on the essentially flat “underside” 12 or rear side of the platform 8 which faces away from the blade airfoil 6 .
  • the fastening elements 14 are visible, which is attached close to the trailing edge of the blade airfoil 6 with regard to the axial direction 16 ; a further fastening element is arranged in the proximity of the leading edge which is no longer shown here.
  • the fastening element 14 is adapted specifically to the mechanical loads which are associated with the hooking in the stator blade carrier.
  • the fastening element 14 is constructed as a separate component which is produced independently from the remaining stator blade 2 and only subsequently connected to it, wherein the material which is used for the fastening element 14 is less resistant to high temperature but on the other hand is tougher than the material from which the blade airfoil 6 and the platform 8 are produced.
  • the fastening element 14 in addition to a fastening hook 18 which projects from the rear side 12 of the platform 8 and is angled approximately at right angles, comprises a connecting plate 20 , with a rectangular base surface, which is formed onto the fastening hook.
  • the connecting plate 20 is fixed in a positive-locking manner in an associated recess 21 of the platform 8 .
  • the connecting plate 20 By its flat bearing surface 22 the connecting plate 20 abuts flat upon the base surface of the recess 21 .
  • the depth of the recess 21 corresponds to the thickness of the connecting plate 20 so that a step-free transition in the edge region to the platform surface is created.
  • two opposite longitudinal edges 24 of the connecting plate 20 are beveled in such a way that they are gripped or enclosed on the edge of the recess 21 on the platform side by projections 26 which are complementary to the longitudinal edges 24 and extend parallel to them.
  • the projections 26 form a guiding and fastening rail which extends perpendicularly to the plane of the drawing and into which the connecting plate 20 is inserted for installing the fastening element 14 .
  • additional fixing means which are not shown here, can be provided.
  • Corresponding bearing and retaining forces are absorbed predominantly by the beveled longitudinal edges 24 of the connecting plate 20 and by the corresponding projections 26 on the platform side.
  • the edge length of the connecting plate 20 being selected to be correspondingly large, the forces which are effective per length section are relatively small and are therefore easily controllable. It is self-evident that the person skilled in the art can modify many of the details of the connection between fastening element 14 and platform 20 without deviating from the principle of the positive locking which is shown in FIG. 1 .
  • the fastening element 14 which is shown in FIG. 2 is similar to the fastening element 14 according to FIG. 1 with its connecting plate 20 arranged in a recessed manner in an associated recess 21 of the platform 8 , but, unlike this, is not fixed in a positive-locking manner. Rather, the connecting plate 20 is connected to the platform 8 in a materially-bonding manner by means of a number of soldered points or soldered joints 28 between the bearing surfaces 22 .
  • soldered points or soldered joints 28 between the bearing surfaces 22 .
  • the selection of the soldering method is essentially influenced by the operating conditions of the soldering, by the material pairing and by the compatibility with other thermal treatment requirements.
  • FIG. 3 shows a variant in which only an outer section 30 of the fastening element 14 is a separately produced component, but the remaining part is formed integrally onto the platform 8 or is cast together with it.
  • the outer section 30 which acts virtually as an “adapter”, has an enclosure 32 which is similar to a sealing cap for a bottle or a pipe, and by which the outer section encloses the component of the fastening element 14 on the platform side on its outer end.
  • the dimensionings are selected in such a way that before introducing a means of joining a loose, clearance-related seat is created which can be adapted to the geometric specifications which exist at the respective place of installation and compensates manufacturing-related tolerances and fluctuations in the process.
  • the two components of the fastening element 14 are interconnected by means of a soldering substance 36 which is introduced into the gap 34 and then solidified.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • External Artificial Organs (AREA)
  • Primary Cells (AREA)
  • Machine Tool Units (AREA)
US12/225,933 2006-04-06 2007-02-21 Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine Expired - Fee Related US8128357B2 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP06007332A EP1843009A1 (fr) 2006-04-06 2006-04-06 Segment d'ailette de guidage d'une turbomachine, procédé de fabrication associé et turbomachine
EP06007332.7 2006-04-06
EP06007332 2006-04-06
PCT/EP2007/051669 WO2007113053A1 (fr) 2006-04-06 2007-02-21 Segment d'aubes fixes d'une turbomachine thermique, procédé de fabrication associé et turbomachine thermique

Publications (2)

Publication Number Publication Date
US20090304503A1 US20090304503A1 (en) 2009-12-10
US8128357B2 true US8128357B2 (en) 2012-03-06

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ID=37075825

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/225,933 Expired - Fee Related US8128357B2 (en) 2006-04-06 2007-02-21 Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine

Country Status (10)

Country Link
US (1) US8128357B2 (fr)
EP (2) EP1843009A1 (fr)
JP (1) JP4782225B2 (fr)
CN (1) CN101460709B (fr)
AT (1) ATE457413T1 (fr)
DE (1) DE502007002816D1 (fr)
ES (1) ES2339717T3 (fr)
PL (1) PL2002085T3 (fr)
RU (1) RU2421624C2 (fr)
WO (1) WO2007113053A1 (fr)

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US9631517B2 (en) 2012-12-29 2017-04-25 United Technologies Corporation Multi-piece fairing for monolithic turbine exhaust case

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EP1970533A1 (fr) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Turbine ayant au moins un rotor comprenant des disques rotoriques et un tirant
DE102008043605B4 (de) * 2007-11-16 2015-05-07 Alstom Technology Ltd. Verfahren zur Herstellung eines Turbinengehäuses
EP2282012B1 (fr) * 2009-07-03 2015-11-25 Alstom Technology Ltd Procédé de remplacement d'un couvercle d'une aube directrice d'une turbine à gaz
FR2976968B1 (fr) * 2011-06-21 2015-06-05 Snecma Piece de turbomachine formant redresseur de compresseur ou distributeur de turbine et procede pour sa fabrication
EP3000980A3 (fr) * 2014-09-29 2016-04-13 United Technologies Corporation Composant hybride comprenant l'alliage gamma tial
US10711637B2 (en) * 2017-06-15 2020-07-14 General Electric Company Turbine component assembly
CN113500479B (zh) * 2021-07-07 2022-06-03 彭忠捷 一种骨科手术钢丝导引钩的自动加工机器人

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EP1149984A2 (fr) 2000-04-25 2001-10-31 General Electric Company Crochet de fixation pour un segment refroidi en circuit fermé d'une tuyère de guidage d'une turbine à gaz
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FR2825780A1 (fr) 2001-06-06 2002-12-13 Snecma Moteurs Architecure de chambre de combustion de turbomachine en materiau a matrice ceramique
RU2204021C2 (ru) 1999-03-01 2003-05-10 Закрытое акционерное общество "Научно-инженерный центр Керамические тепловые двигатели им. А.М. Бойко" Квазиадиабатный керамический сопловой аппарат высокотемпературной газовой турбины (варианты)
EP1462616A2 (fr) 2003-03-22 2004-09-29 MTU Aero Engines GmbH Ensemble de fixation axiale et radiale d'une aube statorique dans un boítier d'une turbine
EP1505259A1 (fr) 2003-08-08 2005-02-09 ROLLS-ROYCE plc Ensemble pour le montage d'un composant non rotatif d'une turbine à gaz

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US2402005A (en) 1944-05-08 1946-06-11 Hans R Amundsen Friction brake or clutch
US2942844A (en) 1952-12-22 1960-06-28 Gen Motors Corp Turbine nozzle
US3072380A (en) 1959-02-05 1963-01-08 Dresser Ind Stator blade carrier assembly mounting
SU859656A1 (ru) 1979-08-27 1981-08-30 Предприятие П/Я А-3513 Направл ющий аппарат турбомашины
US5848854A (en) * 1995-11-30 1998-12-15 General Electric Company Turbine nozzle retainer assembly
RU2204021C2 (ru) 1999-03-01 2003-05-10 Закрытое акционерное общество "Научно-инженерный центр Керамические тепловые двигатели им. А.М. Бойко" Квазиадиабатный керамический сопловой аппарат высокотемпературной газовой турбины (варианты)
EP1149984A2 (fr) 2000-04-25 2001-10-31 General Electric Company Crochet de fixation pour un segment refroidi en circuit fermé d'une tuyère de guidage d'une turbine à gaz
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EP1505259A1 (fr) 2003-08-08 2005-02-09 ROLLS-ROYCE plc Ensemble pour le montage d'un composant non rotatif d'une turbine à gaz

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DE502007002816D1 (de) 2010-03-25
JP2009532623A (ja) 2009-09-10
ES2339717T3 (es) 2010-05-24
PL2002085T3 (pl) 2010-07-30
EP2002085A1 (fr) 2008-12-17
WO2007113053A1 (fr) 2007-10-11
CN101460709B (zh) 2011-11-02
EP2002085B1 (fr) 2010-02-10
ATE457413T1 (de) 2010-02-15
EP1843009A1 (fr) 2007-10-10
JP4782225B2 (ja) 2011-09-28
RU2421624C2 (ru) 2011-06-20
US20090304503A1 (en) 2009-12-10
CN101460709A (zh) 2009-06-17

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